CN112228249B

CN112228249B - Valve structure of liquid rocket engine and rocket engine

Info

Publication number: CN112228249B
Application number: CN202010964200.4A
Authority: CN
Inventors: 李莹; 陈涛; 任志彬; 王喜良; 张思远; 李欢; 刘耀林; 范宇; 杨永刚; 张航; 薛海龙
Original assignee: Landspace Technology Co Ltd
Current assignee: Landspace Technology Co Ltd
Priority date: 2020-09-15
Filing date: 2020-09-15
Publication date: 2021-06-01
Anticipated expiration: 2040-09-15
Also published as: CN112228249A

Abstract

The invention provides a valve structure of a liquid rocket engine, which comprises an actuating cylinder, a first sealing element, a second sealing element, a thrust assembly, a shell and a valve core, wherein the actuating cylinder is arranged on the shell; the inner side of the actuating cylinder is provided with a first channel which is used for the circulation of gas media and penetrates through the two ends of the actuating cylinder and a second channel which has a different extending direction from the first channel; the first sealing element and the second sealing element are sleeved on the surface of the thrust assembly, the outer side surfaces of the first sealing element and the second sealing element are respectively abutted against the inner wall of the actuating cylinder and the inner side of the shell, one end of the thrust assembly is arranged in the actuating cylinder through the first sealing element, the other end of the thrust assembly is used for pushing the valve element located in the shell to move, the second sealing element is located on the inner side of the shell, the first sealing element is used for sealing the inner wall of the actuating cylinder, and the second sealing element is used for sealing the inner wall, close to the end of the actuating cylinder, of the shell to prevent the leakage of switch control gas. Compared with the prior art, the sealing effect is improved, the loss of liquid media is reduced, and the cost is saved.

Description

Valve structure of liquid rocket engine and rocket engine

Technical Field

The invention relates to the technical field of attitude control power system valves, in particular to a valve structure of a liquid rocket engine and the rocket engine.

Background

With the rapid development of the aerospace industry, all the technologies related to the rocket field also realize the rapid advance. The valve is an important part for realizing the starting and shutdown of the liquid rocket engine. The medium of the low-temperature liquid rocket engine is an ultralow-temperature propellant, the medium temperature range is usually about 20K-120K, and the pressure is more than 10 MPa. The valve operating gas is usually a high-pressure gas having a pressure of about 20 MPa.

Liquid propellant used by the existing domestic active low-temperature liquid rocket engine adopts liquid methane as propellant besides liquid hydrogen, liquid oxygen and the like. The valve is usually opened and closed by moving an internal valve, and the valve can be in direct contact with the inner wall of the valve during the movement. For tight sealing, a dynamic sealing element is usually required between the valve and the inner wall of the valve, and may be realized by using a metal bellows or a noble metal-coated sealing ring, for example. The valve is actuated by using high-pressure helium gas, and the valve needs to be kept in a control gas state after being actuated in place. However, the large-size metal corrugated pipe is difficult to form, long in production period, large in space structure, high in purchasing cost, low in service life, poor in reliability and the like.

It is desirable to provide a valve structure suitable for low temperature environment and having a state maintaining function.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a valve structure of a liquid rocket engine and the rocket engine. The valve structure can improve the sealing effect and reduce the loss of liquid medium, thereby improving the working reliability and efficiency of the attitude and orbit control engine.

One aspect of the present invention provides a valve structure of a liquid rocket engine, including an actuator cylinder, a first sealing element, a second sealing element, a thrust assembly, a housing, and a valve core; the inner side of the actuating cylinder is provided with a first channel which is used for gas medium to flow through and penetrates through two ends of the actuating cylinder and a second channel which has a different extending direction from the first channel; the first sealing element and the second sealing element are sleeved on the surface of the thrust assembly, the outer side surfaces of the first sealing element and the second sealing element are respectively abutted against the inner wall of the actuating cylinder and the inner side of the shell, one end of the thrust assembly is arranged in the actuating cylinder through the first sealing element, the other end of the thrust assembly is used for pushing the valve element in the shell to move, and the second sealing element is arranged on the inner side of the shell and close to one end of the actuating cylinder; the shell is of a structure with two communicated ends and a flow channel arranged inside, an annular transition inclined plane is arranged on the inner wall of the part of the flow channel matched with the end part of the valve core to close the medium inlet along the circumferential direction, a convex part matched with the annular transition inclined plane is arranged at the end part of the valve core, the first sealing element is used for sealing the inner wall of the actuating cylinder, and the second sealing element is used for sealing the inner wall of the shell close to the end of the actuating cylinder to prevent the leakage of switch control gas;

open air flow enters through the first channel and is far away from the shell side so as to push the thrust assembly to push the valve core to move towards the direction far away from the actuating cylinder, and the medium inlet is communicated with the first medium outlet;

and the closing air flow acts between the first sealing element and the second sealing element through the second channel to push the thrust assembly and the valve core to move towards the direction close to the actuating cylinder, so that the valve core abuts against the shell and is close to the end of the valve core to enable the medium inlet and the second medium outlet on the shell to be communicated.

In the same embodiment, the first passage comprises a first air passage, a second air passage and a third air passage, and the transition point of the first air passage and the second air passage forms a first step for limiting the movement of the first sealing element to one side of the first air passage; the second vent passage and the transition point of the third vent passage form a second step for limiting the movement of the first sealing element to one side of the third vent passage.

In the same embodiment, the butt end faces of the shell and the actuating cylinder are tightly attached to each other and fixedly connected with each other.

In the same embodiment, a spring and a cover plate are respectively arranged inside and at one end of the shell, the cover plate is located at one end, far away from the actuating cylinder, of the shell, the cover plate is connected with the shell through a bolt, a fixing groove for fixing the spring is formed in the cover plate, an air outlet hole connected with the flow channel is formed in the bottom of the fixing groove, two ends of the spring are respectively connected with the valve core and the fixing groove, and the spring is used for pushing the valve core to move towards one side, far away from the cover plate.

In the same embodiment, the casing comprises a first casing body, a second casing body and a third casing body which are integrally formed and are cylindrical in appearance, two ends of the second casing body are respectively connected with the first casing body and the third casing body, and the other end of the first casing body is matched with the third air passage, so that the circumferential outer surface of the first casing body is tightly attached to the inner wall of the third air passage and fixedly connected with the inner wall of the third air passage.

In the same embodiment, a limiting boss for limiting the second sealing element to move towards the third outer shell is arranged inside the third outer shell, the medium inlet, the first medium outlet and the second medium outlet are located on the third outer shell, the directions of the openings of the medium inlet and the first medium outlet are parallel, the directions of the medium inlet and the second medium outlet are mutually perpendicular, and the axes of the medium inlet and the first medium outlet are not on the same straight line.

In the same embodiment, one end of the valve core is provided with a concave part for matching with the thrust assembly, the spring is positioned at one end of the valve core far away from the concave part, and the inner diameter of the concave part is gradually reduced from top to bottom.

In the same embodiment, one side of each of the first seal and the second seal is respectively and closely attached to the thrust assembly along the circumferential direction of the thrust assembly, the first seal comprises two first seal bodies, and the first seal is a structure that the head parts of the two first seal bodies close to the thrust assembly end are close to each other, and the tail parts close to the actuating cylinder end are far away from each other; the second sealing element comprises two second sealing bodies, the head parts of the second sealing bodies, close to the thrust assembly end, of the second sealing bodies are close to each other, the tail parts, close to the shell inner wall end, of the second sealing bodies are far away from each other, and the first sealing bodies and the second sealing bodies, the actuator cylinder inner wall and the shell inner wall butt end are both in arc shapes.

In the same embodiment, the first sealing element comprises two U-shaped first sealing bodies, the bottoms of the two first sealing bodies close to the thrust assembly end are close to each other, two ends of the U-shaped first sealing body close to the inner wall side of the actuating cylinder are provided with semi-arcs, and the arc top ends of the semi-arcs are abutted with the inner wall of the actuating cylinder; the second sealing member contains two U type second seals, the second sealing member is for being close to two of thrust subassembly end the second seal bottom is close to each other, and is close to the both ends of the U type second seal of casing inner wall side are equipped with the semicircle, the arc top of semicircle with the inner wall butt of casing.

Another aspect of the present invention provides a rocket engine including a valve structure of a liquid rocket engine as described above.

According to the valve structure of the liquid rocket engine and the rocket engine provided by the embodiment of the invention, the first sealing element and the second sealing element are sleeved on the surface of the thrust assembly, and the outer side surfaces of the first sealing element and the second sealing element are respectively abutted against the inner wall of the actuating cylinder and the inner wall of the shell. The first sealing element is used for realizing sealing on the inner wall of the actuating cylinder, and the second sealing element is used for realizing sealing on the inner wall of the shell close to the end of the actuating cylinder so as to prevent the switch control air from leaking along a gap between the inner wall of the actuating cylinder and the first sealing element and a gap between the second sealing element and the inner wall of the shell. The whole structure is reasonable in design, improves the sealing performance, reduces the loss of liquid media, is convenient to process, and can save the cost, thereby further improving the performance of the rocket engine and improving the working reliability and efficiency of the rocket engine.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.

FIG. 1 is a schematic structural diagram of a valve according to an embodiment of the present invention;

FIG. 2 is a schematic view of an actuator cylinder according to an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of a housing according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a valve core in an embodiment of the invention;

FIG. 5 is a schematic structural diagram of a cover plate according to an embodiment of the present invention;

FIG. 6 is a schematic view of the first seal, second seal and thrust assembly in an embodiment of the present invention;

FIG. 7 is a schematic structural diagram of a circular arc shape in an embodiment of the present disclosure;

FIG. 8 is a schematic view of a first seal according to an embodiment of the present invention;

FIG. 9 is a schematic structural diagram of a first seal ring according to an embodiment of the present invention;

FIG. 10 is a schematic structural diagram of a sinking plane and a protruding strip in an embodiment of the present invention;

FIG. 11 is a schematic view of the structure of the first sealing body in the second embodiment of the present invention.

Description of reference numerals:

1 actuator cylinder 2 first seal

3 second seal 4 thrust assembly

5 case 6 valve core

7 first channel 8 second channel

9 annular transition inclined plane 10 convex part

11 opening air flow 12 first medium outlet

13-off gas flow 14 second medium outlet

15 first airway 16 second airway

17 third vent path 18 first step

19 second step 20 spring

21 cover plate 22 fixing groove

23 air outlet 24 first outer shell

25 second housing 26 recess

27 leading and 28 trailing

29 circular arc shape 30 medium inlet

31 limiting boss 32 convex part

33 annular groove 34 first seal

35 lower recess 36 first projection

37 first recess 38 is slotted

39 third outer shell 40 sinking plane

41 convex strip 42 semi-circular arc

Detailed Description

Reference will now be made in detail to various exemplary embodiments of the invention, the detailed description should not be construed as limiting the invention but as a more detailed description of certain aspects, features and embodiments of the invention.

It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.

One aspect of the present invention provides a valve structure of a liquid rocket engine, as shown in fig. 1, 2, 3, 4 and 6, comprising a cylinder 1, a first seal 2, a second seal 3, a thrust assembly 4, a housing 5 and a valve core 6. The actuator cylinder 1 has a first passage 7 for passing a gas medium therethrough and extending through both ends thereof and a second passage 8 extending in a direction different from that of the first passage 7. The first sealing element 2 and the second sealing element 3 are sleeved on the surface of the thrust assembly 4, the outer side surfaces of the first sealing element 2 and the second sealing element 3 are respectively abutted against the inner wall of the actuating cylinder 1 and the inner side of the shell 5, one end of the thrust assembly 4 is arranged in the actuating cylinder 1 through the first sealing element 2, the other end of the thrust assembly is used for pushing the valve core 6 located in the shell 5 to move, and the second sealing element 3 is located on the inner side of the shell 5 and is close to one end of the actuating cylinder 1. The casing 5 is a structure with two communicated ends and a flow passage arranged inside, the flow passage is matched with the end part of the valve core 6 to close the medium inlet, the inner wall of the part of the flow passage matched with the end part of the valve core 6 is provided with an annular transition inclined surface 9 along the circumferential direction, and the end part of the valve core 6 is provided with a convex part 32 matched with the annular transition inclined surface 9. The first seal 2 is arranged to seal against the inner wall of the ram 1 and the second seal 3 is arranged to seal against the inner wall of the housing 5 adjacent the end of the ram 1 to prevent leakage of the switching control gas.

The first air flow 11 enters through the first channel 7 away from the housing 5 side to push the thrust assembly 4 to push the valve element 6 away from the ram 1 to conduct the medium inlet 30 and the first medium outlet 12.

The shut-off gas flow 13 acts between the first seal 2 and the second seal 3 via the second passage 8 to urge the thrust assembly 4 and the valve spool 6 towards the ram 1 to conduct the medium inlet 30 and the second medium outlet 14 in the housing 5 by the valve spool 6 abutting the end of the housing 5 adjacent the valve spool 6.

Specifically, according to the valve structure of the liquid rocket engine and the rocket engine provided by the embodiment of the invention, the first sealing element 2 and the second sealing element 3 are sleeved on the surface of the thrust assembly 4, and the outer side surfaces of the first sealing element 2 and the second sealing element 3 are respectively abutted against the inner wall of the actuating cylinder 1 and the inner wall of the shell 5. The first sealing element 2 is used for sealing the inner wall of the actuating cylinder 1, and the second sealing element 3 is used for sealing the inner wall of the shell 5 close to the end of the actuating cylinder 1 so as to prevent the switch control air from leaking along the gap between the inner wall of the actuating cylinder 1 and the first sealing element 2 and the gap between the second sealing element 3 and the inner wall of the shell 5. The application of the valve structure is that the valve structure is matched with the inner walls of the thrust assembly 4 and the shell 5 by arranging the first sealing piece and the second sealing piece, and the valve structure can reliably realize control over the valve through the switch airflow by arranging the switch airflow channel. The whole structure is reasonable in design, improves the sealing performance, reduces the loss of liquid media, is convenient to process, and can save the cost, thereby further improving the performance of the rocket engine and improving the working reliability and efficiency of the rocket engine.

It should be noted that, as shown in fig. 1 and fig. 2, in the present embodiment, the first passage 7 includes a first air passage 15, a second air passage 16 and a third air passage 17, and when the first sealing member 2 moves, in order to define a moving position of the first sealing member 2 in the first passage 7 to prevent the first sealing member 2 from sliding out of the first passage 7, for example, a transition portion between the first air passage 15 and the second air passage 16 forms a first step 18 for defining the movement of the first sealing member 2 to the side of the first air passage 15. For example, the transition point between the second vent passage 16 and the third vent passage 17 forms a second step 19 for limiting the movement of the first seal member 2 to the third vent passage 17 side. In addition, in order to ensure the smooth flow of the air stream, for example, the axes of the first air passage 15, the second air passage 16 and the third air passage 17 may be arranged on the same straight line.

As shown in fig. 1, 2, 3 and 9, in order to ensure the tight connection between the housing 5 and the ram 1 and reduce the gas flowing out from the gap between the housing 5 and the ram 1, for example, the abutting end faces of the housing 5 and the ram 1 are tightly attached to each other and fixedly connected to each other. For example, the fixed connection may comprise welding, by bolting. In practical application, in order to ensure that the housing 5 and the actuator cylinder 1 are connected more tightly, at least one annular groove 33 may be formed on an end surface of the actuator cylinder 1, which is in butt joint with the housing 5, and a first sealing ring 34 is disposed on the annular groove 33, and a part of the first sealing ring 34 is located in the annular groove 33, and another part is tightly attached to the housing 5. It is worth mentioning that the number of the annular grooves 33 can be increased according to actual requirements to improve the sealing between the housing 5 and the actuator cylinder 1 and reduce the leakage of the air flow.

In this embodiment, a spring 20 and a cover plate 21 are respectively disposed inside and at one end of the housing 5, the cover plate 21 is located at one end of the housing 5 away from the actuator cylinder 1, the cover plate 21 is connected to the housing 5 through a bolt, two ends of the spring 20 are respectively connected to the valve core 6 and the cover plate 21, and when the air flow acts on the valve, the spring 20 is used to push the valve core 6 to move towards the side away from the cover plate 21 rapidly. When the air flow acts on the valve, the spring 20 can play a role in pressure reduction and buffering, damage of the spring and the valve caused by overlarge pressure is avoided, the valve core 6 and the cover plate 21 are ensured to be intact, and the valve is favorable for use.

In order to prevent one end of the spring 20 from sliding during use, as shown in fig. 1, 3, 4 and 5, for example, a fixing groove 22 for fixing the spring 20 is provided on the cover plate 21, so that one end of the spring 20 is located in the fixing groove 22. Furthermore, a concave portion 35 (one end of the concave portion 35 is close to the cover plate 21 and is concave toward the actuator cylinder 1) may be further disposed on the valve core 6, so that one end of the spring 20, which is far away from the cover plate 21, is located in the concave portion 35, thereby ensuring that two ends of the spring 20 are fixed, and preventing the spring 20 from being affected by an elastic force different from the compression and extension directions of the spring 20 and affecting the use effect of the spring 20. In addition, for convenience of gas discharge, for example, an air outlet 23 connected to the flow passage is provided at the bottom of the fixing groove 22.

As shown in fig. 1 and 5, in order to ensure the close contact between the valve element 6 and the cover plate 21 and to prevent the air flow from flowing out from the gap between the valve element 6 and the cover plate 21 when the air flow is open, a first protrusion 36 is provided on the end surface of the side wall at one end of the lower recess 35 of the valve element 6, and a first recess 37 for engaging with the first protrusion 36 is provided on the cover plate 21. The first concave part 37 and the first convex part 36 realize concave-convex fit, so that the valve core 6 and the cover plate 21 are tightly sealed.

As shown in fig. 1, 3 and 10, when the medium inlet 30 is communicated with the second medium outlet 14, in order to ensure that the medium flowing from the medium inlet 30 into the second medium outlet 14 is uniform and reduce the squeezing of the medium to the inner wall of the housing 5, for example, a sinking surface 40 is provided on the side of the valve element 6 close to the medium inlet 30, and the medium flows into the flow channel in the housing 5 along the sinking surface 40. When the medium inlet 30 and the first medium outlet 12 are communicated, the protruding strips 41 provided on the valve body 6 reduce the outflow of the medium from the gap between the medium inlet 30 and the depressed surface 40.

As shown in fig. 1 and 4, in the practical application process, in order to reduce the weight of the valve, a groove 38 may be formed along the circumferential surface of the valve element 6, the length of the valve element is a, and the distance from the groove 38 to the end of the valve element (the end close to the actuator cylinder 1) is B, and a large number of guideline experiments show that when B is greater than or equal to 1/5a and less than or equal to 3/5a, the weight of the valve may be reduced without affecting the sealing effect of the valve.

In the present embodiment, as shown in fig. 1 and 3, the housing 5 includes a first outer housing 24, a second outer housing 25 and a third outer housing 39, which are integrally formed and have a cylindrical shape, and both ends of the second outer housing 25 are connected to the first outer housing 24 and the third outer housing 39, respectively. The first outer housing 24 is tightly connected to the actuator 1 to reduce the air flow from the gap between the first outer housing 24 and the actuator 1. For example, the end of the first outer housing 24 adjacent the ram 1 engages the third vent passage 17 such that the outer circumferential surface of the first outer housing 24 abuts the inner wall of the third vent passage 17. The first outer housing 24 and the actuator cylinder may be fixedly connected (screwed or welded) to the inner wall of the third vent passage 17.

For limiting the second sealing member 3, for example, a limiting boss 31 for limiting the movement of the second sealing member 3 toward the third outer housing 39 is provided inside the third outer housing 39.

In this embodiment, as shown in fig. 1 and 5, the media inlet 30, the first media outlet 12, and the second media outlet 14 are located on the third outer housing 39. For convenience of media exclusion from different outlets, for example, the media inlet 30 and the first media outlet 12 are open in parallel directions, the media inlet 30 and the second media outlet 14 are oriented perpendicular to each other, and the axes of the media inlet 30 and the first media outlet 12 are not collinear.

In practical applications, as shown in fig. 1, 3, 4 and 6, in order to make the thrust assembly 4 quickly engage with the valve core 6 during application, and avoid sliding when contacting with the valve core 6, which would result in the thrust assembly 4 pushing the valve core 6 to move, for example, a recess 26 for engaging with the thrust assembly 4 may be provided at one end of the valve core 6. For example, the inner diameter of the concave portion 26 becomes smaller from the top to the bottom, and the end of the thrust assembly 4, which is engaged with the valve core 6, is located in the concave portion 26 (such that the axis of the thrust assembly 4 is located on the same straight line with the center line penetrating the concave portion 26 in the axial direction) and is in close contact with the concave portion 26, so as to avoid the offset when the thrust assembly 4 pushes the valve core 6.

Further, as shown in fig. 1 and 8, in order to connect the first seal member 2 and the second seal member 3 with the thrust member 4 tightly, the first seal member 2 and the second seal member 3 are fixed firmly, for example, one side of each of the first seal member 2 and the second seal member 3 is closely attached to the thrust member 4 in the circumferential direction of the thrust member 4, and may be fixed to each other by welding.

For example, the first sealing element 2 may comprise two first sealing bodies, and the first sealing element 2 is a structure in which the head portions of the two first sealing bodies near the end of the thrust assembly 4 are close to each other and the tail portions near the end of the actuator cylinder 1 are far from each other. For example, the second seal 3 includes two second seal bodies, and the second seal body has a structure in which the head portions of the two second seal bodies near the thrust member 4 end are close to each other and the tail portions near the inner wall end of the housing 5 are far from each other. For example, the first sealing element 2 includes two first sealing bodies, the cross-sectional profile of the first sealing body along the axial direction of the actuator cylinder 1 is an isosceles trapezoid structure, and the large end faces of the two first sealing bodies are disposed opposite to each other (the large end face corresponds to the tail portion of the first sealing body, the small end face corresponds to the head portion of the first sealing body, the two large end faces are far away from each other, and the two small end faces are close to each other). The second sealing member 3 includes two second sealing bodies, and the cross-sectional shape of the second sealing body along the axial direction of the actuator cylinder 1 is an isosceles trapezoid structure, for example, the second sealing body is similar to the first sealing body in the thrust assembly 4, and therefore, for avoiding redundancy, it is not described one by one.

It should be noted that, as shown in fig. 1 and 7, in order to ensure that the first sealing body and the second sealing body are tightly connected with the inner wall of the actuator cylinder 1 and the inner wall of the housing 5, respectively, and to avoid gas leakage, for example, abutting ends of the first sealing body and the second sealing body with the inner wall of the actuator cylinder 1 and the inner wall of the housing 5 are both in the shape of an arc 29.

In addition, the first seal 2 and the second seal 3 may be sealing plates having a self-tightening functional structure under high pressure. For example, the first sealing element 2 and the second sealing element 3 may be made of a metal material or a non-metal material, and may be used for special conditions such as low temperature and high pressure, and high temperature and high pressure.

As a low-temperature dynamic sealing structure of a liquid rocket engine, the first sealing ring 34 is required to be applicable to the temperature range from minus 268 ℃ to 427 ℃, has stable performance and does not react with most liquid media.

The self-tightening seal of the valve of the present application is described below by taking the first sealing member 2 as an example, specifically as follows: the first seal 2 is mounted on the thrust assembly such that when the first seal 2 is compressed to generate a sealing surface initial sealing force, the first seal 2 deforms to urge the sealing surface against the ram inner wall thereby forming a seal. When the pressure of the sealing medium rises (the actuator cylinder 1 is ventilated, gas enters from the first channel 7 and presses the side of the first sealing element 2 close to the gas inlet end), the pressure borne by the first sealing element 2 is increased, namely the deformation of the first sealing element 2 (the connecting end of the first sealing element 2 and the actuator cylinder) is increased, and the connecting part of the first sealing element 2 and the actuator cylinder 1 is tighter. Therefore, the valve sealing structure has the advantages that the higher the medium pressure is within the allowable sealing pressure range, the better the sealing effect is. I.e. the first seal 2 has a self-tightening effect over a certain pressure range.

The above embodiments may be combined with each other with corresponding technical effects.

The present invention also relates to a second embodiment, as shown in fig. 11, the first sealing element includes two U-shaped first sealing bodies, and the bottom of the first sealing body near the thrust assembly end is close to each other, and two ends of the U-shaped first sealing body near the inner wall side of the actuator cylinder are provided with semi-circular arcs 42, and the arc top ends of the semi-circular arcs 42 are abutted against the inner wall of the actuator cylinder; the second sealing member contains two U type second seals, and the second sealing member is close to each other for two second seal bottoms that are close to thrust unit end, and is close to the both ends of the U type second seal of casing inner wall side and is equipped with the semicircle, the arc top of semicircle and the inner wall butt of casing.

Another aspect of the present invention provides a rocket engine including a valve structure of the above liquid rocket engine.

The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.

Claims

1. The valve structure of a liquid rocket engine is characterized by comprising an actuating cylinder, a first sealing element, a second sealing element, a thrust assembly, a shell and a valve core; the inner side of the actuating cylinder is provided with a first channel which is used for gas medium to flow through and penetrates through two ends of the actuating cylinder and a second channel which has a different extending direction from the first channel; the first sealing element and the second sealing element are sleeved on the surface of the thrust assembly, the outer side surfaces of the first sealing element and the second sealing element are respectively abutted against the inner wall of the actuating cylinder and the inner side of the shell, one end of the thrust assembly is arranged in the actuating cylinder through the first sealing element, the other end of the thrust assembly is used for pushing the valve element in the shell to move, and the second sealing element is arranged on the inner side of the shell and close to one end of the actuating cylinder; the first sealing element is used for sealing the inner wall of the actuating cylinder, and the second sealing element is used for sealing the inner wall of the shell close to the end of the actuating cylinder so as to prevent the switch control gas from leaking; the shell is of a structure with two communicated ends and a flow channel arranged inside, an annular transition inclined plane is arranged on the inner wall of the part of the flow channel matched with the end part of the valve core to close the medium inlet along the circumferential direction, and a convex part matched with the annular transition inclined plane is arranged at the end part of the valve core;

2. The valve structure of a liquid rocket engine according to claim 1, wherein: the first passage comprises a first airway, a second airway and a third airway, the first airway and the second airway transition form a first step for limiting the movement of the first seal to one side of the first airway; the second vent passage and the transition point of the third vent passage form a second step for limiting the movement of the first sealing element to one side of the third vent passage.

3. The valve structure of a liquid rocket engine according to claim 1, wherein: the shell and the butt end face of the actuating cylinder are mutually attached and fixedly connected.

4. The valve structure of a liquid rocket engine according to claim 2, wherein: the valve comprises a shell, an actuating cylinder, a spring, a cover plate, a fixing groove and a flow channel, wherein the spring and the cover plate are arranged at the inner part and one end of the shell respectively, the cover plate is positioned at one end, far away from the actuating cylinder, of the shell, the cover plate is connected with the shell through a bolt, the cover plate is provided with the fixing groove for fixing the spring, an air outlet hole connected with the flow channel is formed in the bottom of the fixing groove, two ends of the spring are connected with the valve element and the fixing groove respectively, and the spring.

5. The valve structure of a liquid rocket engine according to claim 2, wherein: the casing contains integrated into one piece and appearance for columniform first shell body, second shell body and third shell body, second shell body both ends respectively with first shell body with the third shell body is connected, the first shell body other end with the cooperation of third air passage makes the edge the circumference surface of first shell body with the inner wall of third air passage is hugged closely.

6. The valve structure of a liquid rocket engine according to claim 5, wherein: the third shell body is internally provided with a limiting boss for limiting the second sealing element to move towards the third shell body, the medium inlet, the first medium outlet and the second medium outlet are positioned on the third shell body, the opening directions of the medium inlet and the first medium outlet are parallel, the directions of the medium inlet and the second medium outlet are mutually vertical, and the axes of the medium inlet and the first medium outlet are not on the same straight line.

7. The valve structure of a liquid rocket engine according to claim 4, wherein: one end of the valve core is provided with a concave part used for being matched with the thrust assembly, the spring is positioned at one end, far away from the concave part, of the valve core, and the inner diameter of the concave part is gradually reduced from the top to the bottom.

8. The valve structure of a liquid rocket engine according to claim 1, wherein: one side of each of the first sealing element and the second sealing element is tightly attached to the thrust assembly along the circumferential direction of the thrust assembly, each first sealing element comprises two first sealing bodies, and the head parts of the two first sealing bodies close to the thrust assembly end are close to each other, and the tail parts close to the actuating cylinder end are far away from each other; the second sealing element comprises two second sealing bodies, the head parts of the second sealing bodies, close to the thrust assembly end, of the second sealing bodies are close to each other, the tail parts, close to the shell inner wall end, of the second sealing bodies are far away from each other, and the first sealing bodies and the second sealing bodies, the actuator cylinder inner wall and the shell inner wall butt end are both in arc shapes.

9. The valve structure of a liquid rocket engine according to claim 1, wherein: the first sealing element comprises two U-shaped first sealing bodies, the bottoms of the two first sealing bodies close to the thrust assembly end are close to each other, two ends of the U-shaped first sealing body close to the inner wall side of the actuating cylinder are provided with semi-arcs, and the arc top ends of the semi-arcs are abutted to the inner wall of the actuating cylinder; the second sealing member contains two U type second seals, the second sealing member is for being close to two of thrust subassembly end the second seal bottom is close to each other, and is close to the both ends of the U type second seal of casing inner wall side are equipped with the semicircle, the arc top of semicircle with the inner wall butt of casing.

10. A rocket engine, characterized by: a valve structure comprising a liquid rocket engine as defined in any one of claims 1-9.